TM 1-1510-223-10 ONE-ENGINE INOPERATIVE MAXIMUM CRUISE POWER 1700 RPM ISA -20°C WEIGHT® 16,000 POUNDS 14,000 POUNDS TORQUE FUEL TOTAL TORQUE FUEL TOTAL PRESSURE PER FLOW FUEL PER FLOW FUEL ALTITUDE IFAT FAT ENGINE PER FLOW IAS TAS ENGINE PER FLOW IAS TAS ENGINE ENGINE FEET °C °C PERCENT LBS/HR LBS/HR KTS KTS PERCENT   LBS/HR    LBS/HR KTS KTS 0 -3 -5 83 646 646 157 154 83 645 645 161 158 2000 -7 -9 83 628 628 155 157 83 627 627 160 162 4000 -11 -13 83 611 611 153 160 83 610 610 158 165 6000 -14 -17 83 597 597 151 162 83 596 596 156 167 8000 -18 -21 83 584 584 148 164 83 583 583 154 170 10,000 -22 -25 83 573 573 146 166 83 572 572 152 173 12,000 -26 -29 83 562 562 143 168 83 561 561 150 176 14,000 -30 -33 83 552 552 140 170 83 551 551 147 178 16,000 -34 -37 83 545 545 137 172 83 544 544 145 18' 18,000 -38 -41 82 530 530 131 170 82 533 533 141 182 20,000 -42 -45 76 499 499 117 158 78 504 504 134 179 22,000 -46 -49 --- --- --- --- --- 72 471 471 124 172 24,000 -50 -53 --- --- --- --- --- 67 438 438 109 158 26,000 --- --- --- --- --- --- --- --- --- --- --- --- 28,000 --- --- --- --- --- --- --- --- --- --- --- --- 29,000 --- --- --- --- --- --- --- --- --- --- --- --- 31,000 --- --- --- --- --- --- --- --- --- --- --- --- 33,000 --- --- --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT055903 NOTE During  operations  with  ice  vanes  extended,  torque  will  decrease  approximately  7 percentage  points  (E.G.,  67%  7  percentage  points  =  60%),  fuel  flow  will  decrease approximately 25 LBS/HR/ENG, and true airspeed will be reduced approximately 15 knots. Figure 7-129.  One Engine Inoperative Max Cruise Power at 1700 RPM - ISA -20 °C (Sheet 1 of 2)  CA Change 2  7-207